BILSAT-1: power system sizing and design

International Conference on Recent Advances in Space Technologies, 2003. RAST '03. Proceedings of Pub Date : 1900-01-01 DOI:10.1109/RAST.2003.1303900

U. Orlu, G. Yuksel, L. Gomes, K. Hall

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引用次数: 15

Abstract

BILSAT-1 is a 129 kg enhanced microsatellite developed by SSTL with TUBITAK-BILTEN engineers as part of a technology transfer programme. The main objective of the mission is remote sensing. The multispectral imager of the satellite has a 26-meter ground sampling distance at 686 km altitude giving a swath width of 55 km and the panchromatic imager of the satellite with 12-meter ground sampling distance gives a 25 km swath width. The satellite has off-axis pointing capability, provided by the ADCS systems, which (amongst other benefits) reduces the revisit time for any given point on the Earth. The advanced and capable Attitude Determination and Control System including star cameras, sun sensors and rate gyros provide accurate and precise attitude information allowing a very high degree of attitude knowledge. Tetrahedral mounted four reaction wheels on board will make the satellite extremely agile, allowing fast slew maneuvers about its roll and pitch axes. On board the satellite there are additional Turkish payloads, including a Digital Signal Processing payload (GEZGIN), and a low-resolution multi spectral camera (COBAN), and SSTL developed payloads: Dual Control Moment Gyros. Due to the large number of subsystems and payloads, the SSTL enhanced microsatellite power system platform is extended to house more than 50 electronic switches to control subsystem and payload operations. Because of the power generation limitations, payload operations are scheduled in order to keep the battery depth of discharge (DoD) at the design level of 15% (which is dictated by the 5+10 years of extended design lifetime of the satellite), although analyses show that the DoD could reach 20% for some particular orbits where intensive operations are required. Several analyses have been done to increase the orbit average power generation and some structural modifications have been made based on the SSTL enhanced microsatellite platform, such as canting the solar panels to maintain energy balance.

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BILSAT-1:电力系统的尺寸和设计

BILSAT-1是SSTL与TUBITAK-BILTEN工程师开发的129公斤增强型微型卫星，作为技术转让计划的一部分。这次任务的主要目标是遥感。卫星的多光谱成像仪在686公里高度的地面采样距离为26米，从而获得55公里的幅带宽度，卫星的全色成像仪在12米的地面采样距离上获得25公里的幅带宽度。卫星具有离轴指向能力，由ADCS系统提供，(除其他好处外)减少了对地球上任何给定点的重访时间。先进和功能强大的姿态确定和控制系统，包括恒星相机，太阳传感器和速率陀螺仪，提供准确和精确的姿态信息，允许高度的姿态知识。四面体上安装的四个反作用轮将使卫星非常灵活，允许在其滚转轴和俯仰轴上快速旋转机动。在卫星上有额外的土耳其有效载荷，包括一个数字信号处理有效载荷(GEZGIN)和一个低分辨率多光谱相机(COBAN)，以及SSTL开发的有效载荷:双控制力矩陀螺仪。由于大量的子系统和有效载荷，SSTL增强型微卫星动力系统平台扩展到容纳超过50个电子开关来控制子系统和有效载荷的操作。由于发电能力的限制，有效载荷操作的安排是为了保持电池放电深度(DoD)在15%的设计水平(这是由卫星5+10年的延长设计寿命决定的)，尽管分析表明，DoD在一些需要密集操作的特定轨道上可以达到20%。在SSTL增强型微卫星平台的基础上，进行了增加轨道平均发电量的分析，并进行了结构改造，如倾斜太阳能板以保持能量平衡。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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International Conference on Recent Advances in Space Technologies, 2003. RAST '03. Proceedings of

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